Gas turbine combustor

Abstract

A gas turbine combustor comprising a burner including: a plurality of fuel nozzles to supply a fuel; a fuel nozzle plate to supports end portions of the fuel nozzles structurally and being configured to distribute the fuel flowing from an upstream side to the fuel nozzles; and a swirler including a plurality of air holes to supply combustion air, characterized in that the fuel nozzle plate is provided with a fuel nozzle receiving hole to receive the fuel nozzle, and the fuel nozzle plate and the fuel nozzle inserted in the fuel nozzle receiving hole are connected to each other from an upstream side of the fuel nozzle plate by welding.

1 . A gas turbine combustor comprising a burner including:
 a plurality of fuel nozzles to supply a fuel;   a fuel nozzle plate to supports end portions of the fuel nozzles structurally and being configured to distribute the fuel flowing from an upstream side to the fuel nozzles; and   a swirler including a plurality of air holes to supply combustion air,   characterized in that   the fuel nozzle plate is provided with a fuel nozzle receiving hole to receive the fuel nozzle, and   the fuel nozzle plate and the fuel nozzle inserted in the fuel nozzle receiving hole are connected to each other from an upstream side of the fuel nozzle plate by welding.   
     
     
         2 . The gas turbine combustor according to  claim 1 , wherein an upstream portion of the fuel nozzle inserted in the fuel nozzle receiving hole to receive the fuel nozzle is formed to have an outer diameter larger than an outer diameter of a downstream portion of the fuel nozzle. 
     
     
         3 . The gas turbine combustor according to  claim 2 , wherein an upstream portion of the fuel nozzle receiving hole is formed to have an inner diameter larger than an inner diameter of a downstream portion of the fuel nozzle receiving hole. 
     
     
         4 . The gas turbine combustor according to  claim 1 , wherein the fuel nozzle is provided with a flange at an upstream end portion of the fuel nozzle to have an outer diameter larger than an inner diameter of the fuel nozzle receiving hole inserted in the fuel nozzle. 
     
     
         5 . The gas turbine combustor according to  claim 3 , wherein a first stepped portion is provided with an upstream portion of the fuel nozzle receiving hole formed in the fuel nozzle plate to receive the fuel nozzle is formed to have an inner diameter larger than an inner diameter of a downstream portion of the fuel nozzle receiving hole; and
 a second stepped portion is provided with an upstream portion of the fuel nozzle inserted in the fuel nozzle receiving hole is formed to have an outer diameter larger than an outer diameter of a downstream portion of the fuel nozzle, and the second stepped portion of the fuel nozzle abuts against the first stepped portion of the fuel nozzle receiving hole.   
     
     
         6 . The gas turbine combustor according to  claim 3 , wherein a first tapered portion in which an upstream portion of the fuel nozzle receiving hole formed in the fuel nozzle plate is formed to have an inner diameter larger than an inner diameter of a downstream portion of the fuel nozzle receiving hole; and
 a second tapered portion in which an upstream portion of the fuel nozzle inserted in the fuel nozzle receiving hole is formed to have an outer diameter larger than an outer diameter of a downstream portion of the fuel nozzle, and   an outer surface of the second tapered portion of the fuel nozzle abuts against the first tapered portion of the fuel nozzle receiving hole.   
     
     
         7 . The gas turbine combustor according to  claim 1 , wherein a gap is formed between an inner surface of the fuel nozzle receiving hole formed in the fuel nozzle plate to receive the fuel nozzle and an outer surface of the fuel nozzle inserted in the fuel nozzle receiving hole. 
     
     
         8 . The gas turbine combustor according to  claim 1 , wherein a portion of the fuel nozzle projecting to a downstream side from the fuel nozzle receiving hole of the fuel nozzle plate is formed to have an outer diameter being gradually smaller toward a downstream end portion of the fuel nozzle. 
     
     
         9 . The gas turbine combustor according to  claim 1 , wherein the fuel nozzle is provided with an orifice in a fuel passage formed inside the fuel nozzle to narrow the passage.